CN105136391B  A kind of method and system of survey aircraft in ground stress point distance  Google Patents
A kind of method and system of survey aircraft in ground stress point distance Download PDFInfo
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 CN105136391B CN105136391B CN201510454394.2A CN201510454394A CN105136391B CN 105136391 B CN105136391 B CN 105136391B CN 201510454394 A CN201510454394 A CN 201510454394A CN 105136391 B CN105136391 B CN 105136391B
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 238000005303 weighing Methods 0.000 claims abstract description 165
 238000006073 displacement reaction Methods 0.000 claims description 12
 210000001331 Nose Anatomy 0.000 claims description 8
 229910000831 Steel Inorganic materials 0.000 claims description 5
 230000003068 static Effects 0.000 claims description 5
 239000010959 steel Substances 0.000 claims description 5
 230000005484 gravity Effects 0.000 abstract description 9
 238000005259 measurement Methods 0.000 abstract description 7
 238000010586 diagram Methods 0.000 description 1
 230000000694 effects Effects 0.000 description 1
Abstract
The invention discloses a kind of survey aircraft ground stress point distance method and system, by the way that aircraft is drawn to three weighing platforms, the position of point of force application on weighing platform can be easily accurately measured using principle of moment balance, present invention utilizes the advantage that four on each weighing platform weighing sensor stress can carry out independent output, using principle of moment balance, the position of point of force application on weighing platform can easily be accurately measured, the aircraft that this method is measured ground stress point distance for aircraft in the position of the application point of ground actual forces, avoid tradition application tape measure etc. and survey the wire length rather than airplane wheel of length instrument survey aircraft wheel geometric center point to ground practical function point, so as to influence the measurement result of the center of gravity of airplane, therefore this method provides accurate distance parameter to calculate the center of gravity of airplane, it more can guarantee that the center of gravity of airplane data of calculating are accurate, it is credible.
Description
【Technical field】
The invention belongs to aircraft floor guarantee and aircraft weighting field, and in particular to a kind of survey aircraft is in ground stress point
The method and system of distance.
【Background technology】
Aircraft weighting system is sent out with digital intelligent weighing sensor and the intelligentized development of digital weighing system
Exhibition.Although survey aircraft ground stress point distance from traditional tape measuring to current highprecision, high cost laser three
Dimension measurement, no matter how accurate measured data are, and its result is only the wire length of the geometric center point of airplane wheel, and
The wire length of actual point of force application when nonaircraft wheel acts on ground (or weighing platform face), this has necessarily affected the center of gravity of airplane
Measurement result.
【The content of the invention】
It is an object of the invention to overcome it is abovementioned it is not enough there is provided a kind of survey aircraft in the method for ground stress point distance and
System, provides accurate distance parameter, it is ensured that the center of gravity of airplane data of calculating are accurate, credible to calculate the center of gravity of airplane.
In order to achieve the above object, a kind of survey aircraft comprises the following steps in the method for ground stress point distance：
Step one：Prepare three weighing platforms, and set and weigh biography between the upper weighing platform face and lower weighing platform face at four angles of weighing platform
Sensor；
Step 2：Aircraft is drawn to weighing platform table top, aircraft nose wheel is placed on the first weighing platform, two trailing wheels of aircraft
It is respectively placed on the second weighing platform and the 3rd weighing platform；
Step 3：Twodimensional coordinate system is set up on the table top of the first weighing platform, the second weighing platform and the 3rd weighing platform, makes twodimensional coordinate
The Xaxis of system passes through the center of the first weighing platform, and Yaxis passes through the center of the second weighing platform and the 3rd weighing platform；
Step 4：By the table top leveloff of the first weighing platform, the second weighing platform and the 3rd weighing platform, according to Interval static analysis and power
Square equilibrium principle, calculates the point of force application of the first weighing platform, the second weighing platform and the 3rd weighing platform, respectively A (X respectively_{1}, Y_{1})、B
(X_{1}, Y_{1}) and C (X_{1}, Y_{1})；
Step 5：Aircraft can ask line segment length formula to obtain in the distance of ground stress point according to two point coordinates, i.e. BC,
AB and AC；
Step 6：According to BC, AB and AC, by Heron's formula, draw by A (X_{1}, Y_{1})、B(X_{1}, Y_{1}) and C (X_{1}, Y_{1}) institute's group
Into triangle；
Step 7：Aircraft nose wheel point of force application is obtained by triangle area formula vertical to main wheel point of force application line
Apart from AM, according to principles above and BC the and AM values of gained, aircraft can be obtained and respectively take turns the actual point of force application on weighing platform
Distance, i.e. distance of the aircraft in ground stress point.
In the step one, one group of displacement transducer is provided with by the weighing sensor of weighing platform.
In the step 4, the force value of point of force application is F on the first weighing platform_{A}, coordinate is A (X_{1}, Y_{1}), weighing sensor
Force value is respectively F_{Ai}, wherein, i=1,2,3,4, coordinate is respectively A_{i}(X_{1i}, Y_{1i}), wherein, i=1,2,3,4；
The force value of point of force application is F on second weighing platform_{B}, coordinate is B (X_{2}, Y_{2}), the force value of weighing sensor is respectively F_{Bi},
Wherein, i=1,2,3,4, coordinate is respectively B_{i}(X_{2i}, Y_{2i}), wherein, i=1,2,3,4；
The force value of point of force application is F on 3rd weighing platform_{C}, coordinate is C (X_{3}, Y_{3}), the force value of weighing sensor is respectively F_{Ci},
Wherein, i=1,2,3,4, coordinate is respectively C_{i}(X_{3i}, Y_{3i}), wherein, i=1,2,3,4；
For the first weighing platform, obtained with Interval static analysis：
F_{A}=F_{A1}+F_{A2}+F_{A3}+F_{A4}
According to principle of moment balance, square is taken with X, Yaxis respectively, obtained：
F_{A}·X_{1}=F_{A4}·X_{14}+F_{A3}·X_{13}F_{A2}·X_{12}F_{A1}·X_{11}
F_{A}·Y_{1}=F_{A4}·Y_{14}+F_{A3}·Y_{13}+F_{A2}·Y_{12}+F_{A1}·Y_{11}
Similarly, the coordinate for trying to achieve the second weighing platform and the 3rd weighing platform point of force application is respectively：
In the step 5, aircraft according to two point coordinates asks line segment length formula to obtain in the distance of ground stress point：
Similarly, obtain：
In the step 6, it is assumed that BC=c, AC=b, AB=a
Known three length of side asks the Heron's formula of triangle area to obtain：
In the step 7, the vertical range of aircraft nose wheel point of force application to main wheel point of force application line is：
A kind of survey aircraft is in the system of ground stress point distance, including some weighing platforms, and being capable of receiving scale station information
Computer；The weighing platform includes being provided with four weighing and sensings on upper weighing platform face and lower weighing platform face, four angles in lower weighing platform face
Covered with upper weighing platform face on device, weighing sensor, weighing sensor can be by wirelessly transferring data to computer.
The weighing platform uses steel ball and socket arrangement or the float support for " tumbler " structure.
One group is provided with by the weighing sensor of the weighing platform can detect the displacement transducer of weighing platform face displacement.
Compared with prior art, a kind of survey aircraft in the method for ground stress point distance by the way that aircraft is drawn to three
On weighing platform, the position of point of force application on weighing platform can be easily accurately measured using principle of moment balance, present invention utilizes
Four weighing sensor stress on each weighing platform can carry out the advantage of independent output, using principle of moment balance, Ke Yifang
Just the position for accurately measuring point of force application on weighing platform, the aircraft that this method is measured is aircraft in the distance of ground stress point
The position of the application point of actual forces on ground, it is to avoid traditional application tape measure etc. surveys length instrument survey aircraft wheel geometric center
The wire length rather than airplane wheel of point are to ground practical function point, so that the measurement result of the center of gravity of airplane is influenceed, therefore the party
Method provides accurate distance parameter to calculate the center of gravity of airplane, more can guarantee that the center of gravity of airplane data of calculating are accurate, credible.
Further, the present invention has installed one group of displacement transducer additional between the upper weighing platform face and lower weighing platform face of three weighing platforms
Compensate, it is to avoid constraining on weighing platform for undercarriage is discharged, and it is deformed laterally so that weighing platform and sensor
The strong point is shifted over, and have impact on measurement accuracy of the aircraft in the distance of ground stress point.
A kind of survey aircraft ground stress point distance system by the information in computer acquisition weighing sensor, make
Computer can individually be addressed to each weighing sensor in the system, so as to be monitored to every weighing sensor,
Failure is recognized, and can individually handle the weighing information of every digital intelligent weighing sensor, is substantially increased to weigh and is
The control ability of system, flexibility and intelligent, the feature be using principle of moment balance survey aircraft ground stress point away from
From creating condition.
【Brief description of the drawings】
Fig. 1 is that the present invention weighs weighing platform planar two dimensional coordinate system schematic diagram；
Fig. 2 is the structural representation of displacement transducer in weighing platform of the present invention.
【Embodiment】
The present invention will be further described below in conjunction with the accompanying drawings.
Referring to Fig. 1 and Fig. 2, a kind of survey aircraft comprises the following steps in the method for ground stress point distance：
Step one：Prepare three weighing platforms, and set and weigh between the upper weighing platform face 5 and lower weighing platform face 6 at four angles of weighing platform
Sensor 8, is provided with one group of displacement transducer 7 by the weighing sensor 8 of weighing platform, weighing platform using steel ball and socket arrangement or
For the float support of " tumbler " structure；
Step 2：Aircraft is drawn to weighing platform table top, aircraft nose wheel is placed on the first weighing platform 1, after two of aircraft
Wheel is respectively placed on the second weighing platform 2 and the 3rd weighing platform 3；
Step 3：Twodimensional coordinate system is set up on the table top of the first weighing platform 1, the second weighing platform 2 and the 3rd weighing platform 3, makes two dimension
The Xaxis of coordinate system passes through the center of the first weighing platform 1, and Yaxis passes through the center of the second weighing platform 2 and the 3rd weighing platform 3；
Step 4：By the table top leveloff of the first weighing platform 1, the second weighing platform 2 and the 3rd weighing platform 3, power effect on the first weighing platform 1
The force value of point is F_{A}, coordinate is A (X_{1}, Y_{1}), the force value of weighing sensor 8 is respectively F_{Ai}, wherein, i=1,2,3,4, coordinate difference
For A_{i}(X_{1i}, Y_{1i}), wherein, i=1,2,3,4；
The force value of point of force application is F on second weighing platform 2_{B}, coordinate is B (X_{2}, Y_{2}), the force value of weighing sensor 8 is respectively
F_{Bi}, wherein, i=1,2,3,4, coordinate is respectively B_{i}(X_{2i}, Y_{2i}), wherein, i=1,2,3,4；
The force value of point of force application is F on 3rd weighing platform 3_{C}, coordinate is C (X_{3}, Y_{3}), the force value of weighing sensor 8 is respectively
F_{Ci}, wherein, i=1,2,3,4, coordinate is respectively C_{i}(X_{3i}, Y_{3i}), wherein, i=1,2,3,4；
For the first weighing platform 1, obtained with Interval static analysis：
F_{A}=F_{A1}+F_{A2}+F_{A3}+F_{A4}
According to principle of moment balance, square is taken with X, Yaxis respectively, obtained：
F_{A}·X_{1}=F_{A4}·X_{14}+F_{A3}·X_{13}F_{A2}·X_{12}F_{A1}·X_{11}
F_{A}·Y_{1}=F_{A4}·Y_{14}+F_{A3}·Y_{13}+F_{A2}·Y_{12}+F_{A1}·Y_{11}
Similarly, the coordinate for trying to achieve the second weighing platform 2 and the point of force application of the 3rd weighing platform 3 is respectively：
Finally draw the point of force application of the first weighing platform 1, the second weighing platform 2 and the 3rd weighing platform 3, respectively A (X_{1}, Y_{1})、B(X_{1},
Y_{1}) and C (X_{1}, Y_{1})；
Step 5：Aircraft according to two point coordinates asks line segment length formula to obtain in the distance of ground stress point：
Similarly, obtain：
That is BC, AB and AC；
Step 6：According to BC, AB and AC, by Heron's formula, draw by A (X_{1}, Y_{1})、B(X_{1}, Y_{1}) and C (X_{1}, Y_{1}) institute's group
Into triangle area be：
Step 7：Aircraft nose wheel point of force application is obtained by triangle area formula vertical to main wheel point of force application line
It is apart from AM：
According to principles above and BC the and AM values of gained, aircraft can be obtained and respectively take turns the actual point of force application on weighing platform
Distance, i.e. distance of the aircraft in ground stress point.
Referring to Fig. 1, a kind of survey aircraft is in the system of ground stress point distance, including some weighing platforms, and can receive
The computer of weighing platform information；The weighing platform includes being provided with four on upper weighing platform face 5 and lower weighing platform face 6, four angles in lower weighing platform face 6
Covered with upper weighing platform face 5 on individual weighing sensor 8, weighing sensor 8, weighing sensor 8 can be by wirelessly by data transfer
To computer, weighing platform uses steel ball and socket arrangement or the float support for " tumbler " structure, the weighing sensor 8 of weighing platform
Side, which is provided with one group, can detect the displacement transducer 7 of the displacement of weighing platform face 5.
One weighing table is fixed and, it is known that float support by four or many weighing sensor float supports and position
Use steel ball and ballandsocket or " tumbler " structure, after aircraft is towed on table top, undercarriage is constrained in
Discharged on weighing platform, it is deformed laterally so that table top is shifted over the digital intelligent weighing sensor strong point, shadow
Measurement accuracy of the aircraft in the distance of ground stress point is rung.Therefore, must following table in the horizontal X, Ydirection of each table top it
Between install displacement transducer additional and compensate, to ensure range measurement accuracy of the aircraft in ground stress point.
Claims (8)
1. a kind of survey aircraft is in the method for ground stress point distance, it is characterised in that comprise the following steps：
Step one：Prepare three weighing platforms, and set and weigh between the upper weighing platform face (5) at four angles of weighing platform and lower weighing platform face (6)
Sensor (8)；
Step 2：Aircraft is drawn to weighing platform table top, aircraft nose wheel is placed on the first weighing platform (1), two trailing wheels of aircraft
It is respectively placed on the second weighing platform (2) and the 3rd weighing platform (3)；
Step 3：Twodimensional coordinate system is set up on the table top of the first weighing platform (1), the second weighing platform (2) and the 3rd weighing platform (3), makes two
The Xaxis of dimension coordinate system passes through the center of the first weighing platform (1), and Yaxis passes through the center of the second weighing platform (2) and the 3rd weighing platform (3)；
Step 4：By the first weighing platform (1), the second weighing platform (2) and the 3rd weighing platform (3) leveloff, according to Interval static analysis and power
Square equilibrium principle, calculates the point of force application of the first weighing platform (1), the second weighing platform (2) and the 3rd weighing platform (3), respectively A respectively
(X_{1}, Y_{1})、B(X_{1}, Y_{1}) and C (X_{1}, Y_{1})；
The force value of point of force application is F on first weighing platform (1)_{A}, coordinate is A (X_{1}, Y_{1}), the force value of weighing sensor (8) is respectively
F_{Ai}, wherein, i=1,2,3,4, coordinate is respectively A_{i}(X_{1i}, Y_{1i}), wherein, i=1,2,3,4；
The force value of point of force application is F on second weighing platform (2)_{B}, coordinate is B (X_{2}, Y_{2}), the force value of weighing sensor (8) is respectively
F_{Bi}, wherein, i=1,2,3,4, coordinate is respectively B_{i}(X_{2i}, Y_{2i}), wherein, i=1,2,3,4；
The force value of point of force application is F on 3rd weighing platform (3)_{C}, coordinate is C (X_{3}, Y_{3}), the force value of weighing sensor (8) is respectively
F_{Ci}, wherein, i=1,2,3,4, coordinate is respectively C_{i}(X_{3i}, Y_{3i}), wherein, i=1,2,3,4；
For the first weighing platform (1), obtained with Interval static analysis：
F_{A}=F_{A1}+F_{A2}+F_{A3}+F_{A4}
According to principle of moment balance, square is taken with X, Yaxis respectively, obtained：
F_{A}·X_{1}=F_{A4}·X_{14}+F_{A3}·X_{13}F_{A2}·X_{12}F_{A1}·X_{11}
F_{A}·Y_{1}=F_{A4}·Y_{14}+F_{A3}·Y_{13}+F_{A2}·Y_{12}+F_{A1}·Y_{11}
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</mrow>
<mrow>
<msub>
<mi>Y</mi>
<mn>3</mn>
</msub>
<mo>=</mo>
<mfrac>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>4</mn>
</mrow>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>Y</mi>
<mn>34</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>3</mn>
</mrow>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>Y</mi>
<mn>33</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>2</mn>
</mrow>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>Y</mi>
<mn>32</mn>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>1</mn>
</mrow>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>Y</mi>
<mn>31</mn>
</msub>
</mrow>
<mrow>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>1</mn>
</mrow>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>2</mn>
</mrow>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>3</mn>
</mrow>
</msub>
<mo>+</mo>
<msub>
<mi>F</mi>
<mrow>
<mi>C</mi>
<mn>4</mn>
</mrow>
</msub>
</mrow>
</mfrac>
<mo>;</mo>
</mrow>
Step 5：Aircraft can ask line segment length formula to obtain in the distance of ground stress point according to two point coordinates, i.e., BC, AB and
AC；
Step 6：According to BC, AB and AC, by Heron's formula, draw by A (X_{1}, Y_{1})、B(X_{1}, Y_{1}) and C (X_{1}, Y_{1}) constituted
Triangle；
Step 7：Aircraft nose wheel point of force application is obtained to the vertical range of main wheel point of force application line by triangle area formula
AM, according to principles above and BC the and AM values of gained, can obtain aircraft respectively take turns actual point of force application on weighing platform away from
From i.e. distance of the aircraft in ground stress point.
2. a kind of survey aircraft according to claim 1 is in the method for ground stress point distance, it is characterised in that step one
In, it is provided with one group of displacement transducer (7) by the weighing sensor (8) of weighing platform.
3. a kind of survey aircraft according to claim 1 is in the method for ground stress point distance, it is characterised in that step 5
In, aircraft according to two point coordinates asks line segment length formula to obtain in the distance of ground stress point：
<mrow>
<mi>B</mi>
<mi>C</mi>
<mo>=</mo>
<msqrt>
<mrow>
<msup>
<mrow>
<mo>(</mo>
<msub>
<mi>X</mi>
<mn>2</mn>
</msub>
<mo></mo>
<msub>
<mi>X</mi>
<mn>3</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<msub>
<mi>Y</mi>
<mn>2</mn>
</msub>
<mo></mo>
<msub>
<mi>Y</mi>
<mn>3</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
</mrow>
</msqrt>
</mrow>
Similarly, obtain：
<mrow>
<mi>A</mi>
<mi>B</mi>
<mo>=</mo>
<msqrt>
<mrow>
<msup>
<mrow>
<mo>(</mo>
<msub>
<mi>X</mi>
<mn>1</mn>
</msub>
<mo></mo>
<msub>
<mi>X</mi>
<mn>2</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<mi>Y</mi>
<mo></mo>
<msub>
<mi>Y</mi>
<mn>2</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
</mrow>
</msqrt>
</mrow>
<mrow>
<mi>A</mi>
<mi>C</mi>
<mo>=</mo>
<msqrt>
<mrow>
<msup>
<mrow>
<mo>(</mo>
<msub>
<mi>X</mi>
<mn>1</mn>
</msub>
<mo></mo>
<msub>
<mi>X</mi>
<mn>3</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<mi>Y</mi>
<mo></mo>
<msub>
<mi>Y</mi>
<mn>3</mn>
</msub>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
</mrow>
</msqrt>
<mo>.</mo>
</mrow>
4. a kind of survey aircraft according to claim 3 is in the method for ground stress point distance, it is characterised in that step 6
In, it is assumed that BC=c, AC=b, AB=a
Known three length of side asks the Heron's formula of triangle area to obtain：
<mrow>
<mi>S</mi>
<mo>=</mo>
<mfrac>
<mn>1</mn>
<mn>4</mn>
</mfrac>
<msqrt>
<mrow>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>b</mi>
<mo>+</mo>
<mi>c</mi>
<mo>)</mo>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>b</mi>
<mo></mo>
<mi>c</mi>
<mo>)</mo>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>c</mi>
<mo></mo>
<mi>b</mi>
<mo>)</mo>
<mo>(</mo>
<mi>b</mi>
<mo>+</mo>
<mi>c</mi>
<mo></mo>
<mi>a</mi>
<mo>)</mo>
</mrow>
</msqrt>
<mo>.</mo>
</mrow>
5. a kind of survey aircraft according to claim 4 is in the method for ground stress point distance, it is characterised in that step 7
In, the vertical range of aircraft nose wheel point of force application to main wheel point of force application line is：
<mrow>
<mi>A</mi>
<mi>M</mi>
<mo>=</mo>
<mfrac>
<mn>1</mn>
<mrow>
<mn>2</mn>
<mi>c</mi>
</mrow>
</mfrac>
<msqrt>
<mrow>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>b</mi>
<mo>+</mo>
<mi>c</mi>
<mo>)</mo>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>b</mi>
<mo></mo>
<mi>c</mi>
<mo>)</mo>
<mo>(</mo>
<mi>a</mi>
<mo>+</mo>
<mi>c</mi>
<mo></mo>
<mi>b</mi>
<mo>)</mo>
<mo>(</mo>
<mi>b</mi>
<mo>+</mo>
<mi>c</mi>
<mo></mo>
<mi>a</mi>
<mo>)</mo>
</mrow>
</msqrt>
<mo>.</mo>
</mrow>
6. the system that a kind of survey aircraft described in claim 1 is used in the method for ground stress point distance, its feature exists
In, including some weighing platforms, and it is capable of the computer of receiving scale station information；The weighing platform includes upper weighing platform face (5) and lower weighing platform
It is provided with face (6), four angles of lower weighing platform face (6) on four weighing sensors (8), weighing sensor (8) covered with upper scale
Table top (5), weighing sensor (8) can be by wirelessly transferring data to computer.
7. the system that a kind of survey aircraft according to claim 6 is used in the method for ground stress point distance, it is special
Levy and be, the weighing platform uses steel ball and socket arrangement or the float support for " tumbler " structure.
8. the system that a kind of survey aircraft according to claim 6 is used in the method for ground stress point distance, it is special
Levy and be, the displacement transducer of weighing platform face (5) displacement can be detected by being provided with one group by the weighing sensor (8) of the weighing platform
(7)。
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